Platform cooling arrangement in a turbine component and a method of creating a platform cooling arrangement

Abstract

A method of creating a cooling arrangement for a turbine component, and a cooling arrangement are provided. The turbine component includes an interior cooling passage formed therein. The method comprises a step of forming a slot through a sidewall of the turbine component. The method further comprises a step of forming an insert having one or more cooling features and a cavity. The method further comprises a step of positioning the insert within the slot. The method further comprises a step of securing the insert within the slot. The method further comprises a step of forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.

What is claimed is: 
     
         1 . A method of creating a cooling arrangement for a turbine component having a surface, wherein the turbine component includes an interior cooling passage formed therein, the method comprising steps of:
 forming a slot through a sidewall of the turbine component;   forming an insert having one or more cooling features and a cavity;   positioning the insert within the slot;   securing the insert within the slot; and   forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.   
     
     
         2 . The method of  claim 1 , wherein the sidewall is a sidewall other than a slashface. 
     
     
         3 . The method of  claim 1 , wherein the step of forming the insert comprises an additive manufacturing process selected from the group consisting of direct metal laser melting, direct metal laser sintering, casting, 3D printing, fabrication, and combinations thereof. 
     
     
         4 . The method of  claim 1 , wherein the step of securing the insert within the slot comprises a process selected from the group consisting of mechanical joining, brazing, welding, and combinations thereof. 
     
     
         5 . The method of  claim 1 , wherein the insert comprises a metal selected from a nickel based superalloy, a cobalt based superalloy, a titanium based super alloy, and combinations thereof. 
     
     
         6 . The method of  claim 1 , wherein the insert is the same material as the turbine component. 
     
     
         7 . The method of  claim 1 , wherein the insert is arranged and disposed to provide impingement cooling on an inner surface of the slot. 
     
     
         8 . The method of  claim 1 , wherein the insert comprises an impingement surface, the impingement surface comprising the one or more cooling features. 
     
     
         9 . The method of  claim 8 , wherein the insert is in fluid communication with an exterior surface of the turbine component through at least one passage. 
     
     
         10 . The method of  claim 1 , wherein the turbine component is selected from the group consisting of nozzle, blade, shroud, combustor liner, and combinations thereof. 
     
     
         11 . A cooling arrangement in a turbine component having a surface, wherein the turbine component includes an interior cooling passage formed therein, the cooling arrangement comprising:
 a slot formed through a sidewall of the turbine component;   an insert secured within the slot, the insert having one or more cooling features and a cavity; and   at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.   
     
     
         12 . The cooling arrangement of  claim 11 , wherein the sidewall is a sidewall other than a slashface. 
     
     
         13 . The cooling arrangement of  claim 11 , wherein the insert is formed via an additive manufacturing process selected from the group consisting of direct metal laser melting, direct metal laser sintering, casting, 3D printing, fabrication, and combinations thereof. 
     
     
         14 . The cooling arrangement of  claim 11 , wherein the insert is secured to the sidewall via a process selected from the group consisting of mechanical joining, welding, and combinations thereof. 
     
     
         15 . The cooling arrangement of  claim 11 , wherein the insert comprises a metal selected from a nickel based superalloy, a cobalt based superalloy, a titanium based super alloy, and combinations thereof. 
     
     
         16 . The cooling arrangement of  claim 11 , wherein the insert is the same material as the turbine component. 
     
     
         17 . The cooling arrangement of  claim 11 , wherein the insert is arranged and disposed to provide impingement cooling on an inner surface of the slot. 
     
     
         18 . The cooling arrangement of  claim 11 , wherein the insert comprises an impingement surface, the impingement surface comprising the one or more cooling features. 
     
     
         19 . The cooling arrangement of  claim 18 , wherein insert is in fluid communication with an exterior surface of the turbine component through at least one passage. 
     
     
         20 . The cooling arrangement of  claim 11 , wherein the turbine component is selected from the group consisting of nozzle, blade, shroud, combustor liner, and combinations thereof.